Analysis and reduction of skin-friction in a rocket-based combined-cycle engine flow path operating from Mach 1.5 to 6.0

Wang, Shuai; He, Guoqiang; Yan, De-kun; Huang, Zhiwei; Qin, Fei

doi:10.1016/j.actaastro.2018.06.028

Cited by 12 publications

(1 citation statement)

References 23 publications

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“…This kind of vehicle takes off horizontally, sends payloads to a low Earth orbit, and returns back for a runway landing. An air‐breathing–based combined‐cycle engine is installed on the vehicle to adapt to altitude, which usually varies from zero to tens of kilometers. In addition, a lift‐body configuration is applied to facilitate endoatmospheric flight, which affords the lateral maneuver and helps to revise the trajectory to compensate for the deviation in launch time.…”

Section: Introductionmentioning

confidence: 99%

Ascent trajectory optimization for air‐breathing vehicles in consideration of launch window

Hong-yu

Wang

Cui

2019

Optim Control Appl Methods

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Summary This paper studies the optimal ascent trajectory for a one‐stage‐to‐orbit, air‐breathing vehicle. This kind of vehicle allows endoatmospheric lateral maneuver and thus can extend the launch window. To obtain the optimal orbit‐insertion trajectory in consideration of launch time, a novel optimization model is proposed by designing longitudinal and lateral profiles separately. The longitudinal flight aims to meet the orbital shape that contains the eccentricity and the angular momentum, which are transformed to boundary constrains in altitude, path angle, and velocity. For lateral motion, the orbit inclination and right ascension of ascending node are designed to vary simultaneously as the range. By designing an altitude profile, the terminal altitude and path angle are naturally met and removed from the constraints and accurate orbit insertion is realized by searching the total range and the initial azimuth. Then, the original problem is converted to a parameter optimization problem and solved by a hybrid optimization algorithm, in which the solution is first searched by a particle swarm optimization method and then refined by a modified golden section method. Simulation tests the proposed method with various scenarios. Compared to traditional launch vehicles, a launch window over 1.5 hours is derived without consuming the propellant in the upper stage.

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Section: Introductionmentioning

confidence: 99%